Aeroplane



May 20,1924. 1,495,031

J. F. MUZlK AEROPLANE Filed May v 1921 4 sheets-sheet 1 J. F. M UZIK AEROPLANE May 20, 1924,

4 Sheets-Shee t 2 Filed May '7, 1921 ji a May 20 1924 J. F. MUZIK AI ZROPLANE Filed May '7, 1921 4 Sheets-Sheet 5 Patented May 20, 1924.

UNITED STATES H E. Berna, uew r a AnnoP AnE.

- application and ma -7, 1921. SerialNo. 467,551.

To all whom it may concern: I

Be it known that I, JOHN .M q

- citizen of the United States, residing at Buffalo, in the county of Erie andState of New York, have invented certain new and useful Improvements in Aeropl'ane's, of.

which the following is a specification.

My invention contemplates the .produc-- tion of a new and improvedv aeroplane, and it has for oneof its objects the provision of means for increasing the lifting power of the lifting planes.

It further has for its object the p'rovision of means applied to the lifting planes whereby the lifting power of said planes are increased, fwher'eby increased speed=' is assured, and. at the sametime stabilization, of the aeroplane.

A still further-object of my inventi'on is complete to provide. an aeroplane'in which the-respectlve air-impinging" surfaces are, relatively. arranged in animproved manner, as-

suring greater speed andpower, and to -po-- sition the propeller andpower' medium-in a new andnovel manner.

V\ ith the above and other objects in view,-

3 the invention consists in the'no'vel construct1on, arrangement and combination of parts to be hereinafterdescribeld an'd more particularly, pointed out claims. In the drawings Fig. 1 is a side elevatlon of an;-aeroplane I car a or body, are uprights 20, three sets of embodying the various features of my invention in what I now considerits pre p form' of aeroplane-shown, eachmetcomprrsferred form.

Fig. 2 is a plan view the aeroplane.

Fig. 3 is a Fig.4 is an enlarged longitudinal section taken on line 4-4, Fig. 3.

of a 1 portion of Fig. 5 is an enlargedtransverse section 1 beams or member-s21 rQOII-DGCtIIIg the upper taken on line 5-5, Fig. 2. V I Fig. 6 is a longitudinal section-taken'on line 6-6, Fig. 5, looking in the direction of the arrow crossing said line. j

Fig. 7 is a plan view ofa portion of one of the lifting planes, showing a modified form of air-controlling wings thereon."

Fig. .8 is a'front edge view-'ofthe -planeshown in Fig. 7,

Fig. 9 is a plan view ofa portion of one *of the lifting-planes, showing a still f-u-rfin the {sub joined front elevation" of the s'ame.-

-- Fig. is an edge View-pf theiplane i -shown in Fig.9. I

1 -'Fig. 11 is.a plan 'v-1ewof'one of the ing. planes, with: a still furthermodified form of air+controlling Wings. thereon.

' Fig. 12 is a front edge view-of the lifting planeshown-ji'n Fig. 1.1.

iMy lmp-roved aeroplane; is shown 1 n the d raw-lugs as hav1nga car or passenger housing and three sets of planes, and althou h theplane so constructed.is-believed to e highly efficient in action, it; is.not my. in-

tentionflto limit myself to an; -a,eroplane of this type,: as certain features; of a my jnvent1on may be embodied in :any kind of aero- -mac'h1ne..'-

- i .Th'e'reference numeral :15; designates the ear or body of the aeroplane-designed; to accommodate a? number, of passengers; the car a 'suitable framework 119 'extendi-ng "from the car. or zbody i'lo. It; isof-1course to be understood that-a body: or fuselagewof boat- .for ni or anyv other=.desi-red; form may {be substituted forthe. car .01 bodyshown. The walls of the car =orbody, are, of course built aaround-zasuitable frame or structure, which may .be varied and "forms no partof my invention. 1 However, rising from the car or;body-, o-r,from"thetframe-workaof said nprights 4 being employed in the particular ing four uprights and .twoofeach set being arranged attach side of. the cair or body and extending upwardly. therefrom. The-uprights rising. from each ,s'ide oftthe body are: "connected togethenby longitudinal beams or "members 21, '22, the. longitudinal ends-of the -;uprights, while the .longitu'di- V -nal beams or members L22 connect said -.uprights together at a suitableipoint between thebeamsdon members 21 andthe car or body, said longitudinal beams or {members QQ-being, h'oWeven-pfieferablyarranged close the rat the .aI-Ihelongitud'nal.beamsfor members at opl r' J fli -h l ilg t dinalfien er .9 th

in pairs at each side of the superposed frame, the plane 29 of each set being above I, and paired with the plane 31 and the plane 30 being above and paired with the. plane 32. Said planes extending laterally from the superposed frame, in opposite directions,

the two pairs of each set being spaced apart directly above thev car or body 15. The. two pairs of planes of each set may be re-- 'ferred to as bi-planes spaced apart in the usual manner, the upper planes 29 and 30 being supported from the lower planes 31 and 32 by means of struts 33.

One set of lifting or sustainmg planes is arranged at or near the front end ofthe-car or body, a second set at or near the rear end thereof, and the third set centrally between the first "and second sets. ingor sustaining planes may be constructed in any approved manner, the two upperplanes of each set being secured tofor including in their construction, spars 34 which extendtransversely across the aeroplane, and are'secured to or constructed with g the frame-work of the lifting or sustaining planes in the usual way, alined planes of each set at opposite sides of' the car or body having two spars which are secured to the longitudinal beams or members 21 or 22 of the superposed frame by means of clips 35, or otherwise, the rear spar of each two alined planes being secured to the-bottom of one of the longitudinal beams while the front spar is secured to the top of said beam, as clearly shown'in Fig. 4.

' The lifting or sustaining planes have the *us'ual outline; that is, they are convex on the j upper side and concave at the lower side,- [and by arranging the spars at the front of the planes above the longitudinalbeams or members 21 or 22, as the case may be, and

the spars at the rear below said beams or "members, the planes are'given a proper angleof incidence. It is of courseuhderstood that the pl'anesmay be otherwise secured to the superposed frame and "still have the spars. thereof positioned to provide planes with the proper angle of incidence,

but I considerthe arrangement andtconfstru'ction describedto be simple, inexpensive,

- and highly eflicie'nt' I 5 7' Each of the lifting-or sustaining planesis providedwith one or more "air-controlling wings 36 which extend from the upper con= ranged. s In the open'space within the superposed vex surface of the plane and also from the lower concave surface thereof. :These wings range from the front to the rear edge of the lifting planes, and in preferred form, each is curved so as to have an inner concave and an outer convex surface, as best shown in Fig. 2, the wings being arranged parallel and set obliquely lengthwise so that the front end thereof is farther from the longitudinal center of the aeroplane than the rear end, each wing having preferably the same camber and chord as the main wmgs, and also the same angle of incidence. They are also preferably set at an angle or in clined inwardly toward their upper ends, and each comprises a suitable frame-work 37 supported on sleeves 38 having obliquelydisposed flanges 39, the angle of the flanges determining the angle at which the air-controlling wings are disposed, due to the fact that the frame-work 37 of each of said wings is forced against the flange or flanges of the associated sleeves, as clearly shown in' Fig.

otherwise secured to the spars 34: extending lengthwise through the" lifting or sustaining planes and the air-controlling wings; are

' maintained rigidly on the lifting or sustain- These lifting planes by means of wires 40. i The a1r currentspassmgunderand over the liftlng or sustaming planes come in contact-with theinner sides of the wings 36 and are broken up thereby. In this manner,

cross currents of air are created which produce a forward thrust and a lifting effect on said wings, thus giving the aeroplane greater forward thrust and consequently more speed and also more lifting power.

By-curving said wings and thereby creating an angle of incidence conforming to the angle of incidence of the lifting planes from which they project, and by arranging said wings at an angle transversely, side slip of the currents of air on the lifting planes;

is prevented. Moreover, said wings act'as stabilizing means, since the cross currents of air created by the air currents coming in cont'act with the "wings 36 are forced to- -5. The flanged sleeves 38 are pinned or;

ward the center of the aeroplane within and above the superposed frame, which frame provides a substantially open space except at the point where the elevating planesfand rudders, to be presently described, are arframe. which extends the full length of the aeroplane, two elevators 41, 4c2 and two rudders 413,44 are'arranged; the, elevator 41 being positioned between the two pairs of l lifting or sustaining planes at the front and the second elevator 42 being positioned between the two pairs of lifting planes at the rear, while the rudder a3 is arranged at the extreme front end of the su erposed frame directly in advance of the sevator s1 and iao "'iiitpai the rudder 44 is arranged at eiitrfiie p rear of the frame directly in rear of the elevator 42.

points closer to their; front ends than their rear ends, and they are adapted tobeop'erated in any approved manner, the operation thereof causing the front ends to be raised or lowered, depending upon whether the aeroplane is to ascend o-rdescend. YAs elevators for aeroplanes are not broadly new, varlous means are in common use for operating the same; I, therefore, have not considered it necessary to disclose any means i g V V glp me d? may be. operated independently or in unison, 1""

for this purpose. and it is apparent that they as may be desired. V.

Each'of the elevators has wings 46, which extend upwardly and downwardly therefrom, these wings being arranged at a slight angle to the longitudinal center of the elevator so that during the forward movement of the aeroplane the air currents will impinge thereagainst. These wings differ from the wings of the lifting or sustaining planes in that they are arranged vertically or in perpendicular position, with their rear ends closer to the longitudinal center of the elevator than their front ends. The angle of incidence of said wings thus formed serves to prevent currents of air passing over or under the elevators, as the case may be, sidewise, thus giving the elevators more power and assuring a quicker ascent or descent.

Each of the rudders is provided at opposite sides with wings 47 having a slight angle of incidence, the front ends of the wings sloping downward rearwardly so that the air currents coming in contact with the rudders will have a greater gripping or impinging effect thereagainst, thus giving the rudders more power and making them more responsive so as to cause the aeroplaneto be directed in a circular path with greater speed. The elevators 41 and 42 and the rudders 43 and 44 may be considered broadly as directional means, each of the members forming said directional means having aircontrolling wings thereon, for the purposes stated.

I have illustrated in the drawings four propellers 48, one of which is arranged in rear of each pair of the front and intermediate set of lifting or sustaining planes, these propellers being secured on shafts 49 supported in any suitablemanner and driven from motors (not shown) arranged, if desired. in rear of each pair of lifting or sus-" taining planes of the front and intermediate sets, or within the car or body 15 with suitable transmission means from the motors to the propeller shafts. As the particular manner of supporting and positioning the I motors forms no part of my invention, I do farm or emaronin win '50; applied to a lifting or sustaining plane' In this in II QHI Q a h i wifigsit id 'el t n her -hik ei 'r r ed n e-e ee i an-a1 .vidth 'Qr said plane a arranged ef air currents. The tion, are arranged V a V y I a andthey have thesame camber, chord, and anslamming: dra e mn rmm' w h theyekgterid; While they serveto increase in V the Iifting planeS, they nevertheless act in other respects similar to the preferred construction of wings shown in the preceding figures of the drawings; that is, they will give the lifting wings a greater forward thrust and consequently increase the speed of the aeroplane. They also act to break up the air currents passing over and under the lifting or sustaining planes and create cross currents of air and direct them toward the open center of the aeroplane, thus giving a stabilizing effect. In Figs. 9 and 10 another modification of controlling wing is shown applied to a lifting or sustaining plane. These wings are the same in all respects as the preferred form of wing shown in Figs. 1 to 6, with the exception that each wing, designated by the numeral 51, is fiat and not curved as in the main construction. This construction and arrangement of wing increases the speed of the aeroplane and assists in the lifting power of the lifting or sustaining planes, at the same time serving as stabilizing means.

In Figs. 11 and 12 I have shown air-controlling wings 52, which are arranged at an fort angle transversely, but are disposed in a straight line from front to rear of the lifting or sustaining plane, from which they project; the wings thus being parallel with 'of a mbnoplane, or to the planes of a bi-plane, or any other; type of aeroplane; also that the air-controlling wings 1 aware-em opellerfs rranged as e' s' hw 1:6 provi a may be applied to elevators and rudder ar 7 ranged in a manner different than herein shown and described, as the effect of the air currents thereon will be the same in all cases.

7' Where in the appended claims theword fuselage isemployed, it is intended to mean a car or body of the type shown in the drawings, or any other form of housin'g'or sup ort adapted for use on land or sea;

1-. aving thus describedmyinventi0n,what I-claim is:- I f 1. An aeroplane having a plane provided with a convex upper surface and a concave lower surface, and fair-controlling- I wings ranging, from the front to the rear edge of said plane, saidair-controlling wings.hav ing the same camber, chord and angle of'incidence as said lifting planes;

2; An aeroplane having a plane provided with a convex upper surface and a concave lower surface, and air-controlling Wings ranging from the front to the rear edge of said plane, said air-controlling wings having the, same camber, chord and angle'of nas'pai incidence as said lifting planes andbeing arranged at an angle'transversely.

An'aeroplane having a plane provided with cross wings disposed transversely thereon and arranged diagonally and at an wings serving to break up the currents of air W111 h flow under and over said plane and icre'ating cross currents of air which produce a forward thrust andilift on said wings so as to give the plane more forward thrust, greater lifting power and more speed.

'4; An aeroplane having a plane provided 'witli transverse wings arranged diagonally ture. 7

JOHN F. MUZIK.

25 angle tothe surface of said plane, said 

